archer ii - mfu-pilotenclub28 - 8390087 oe-kbs 21.04.2018 added afms fuel stc 05.07.2018 added afms...

ARCHER IIPA-28-181

PILOT’SOPERATINGHANDBOOK

AND

FAA APPROVEDAIRPLANE FLIGHT MANUAL

FAA APPROVED I N NORMAL AND UTILITY CATEGORIES BASED ON CAR 3. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR 3 AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES.

AIRPLANE AIRPLANESERIAL NO. ________________________ REGIST. NO. _____________________

PA-28-181REPORT: VB-1120 FAA APPROVED BY: ________________________________

WARD EVANSD.O.A. NO. SO-1

DATE OF APPROVAL: PIPER AIRCRAFT CORPORATIONJULY 2, 1979 VERO BEACH, FLORIDA

28 - 8390087 OE-KBS

21.04.2018 added AFMS Fuel STC05.07.2018 added AFMS G5 Instrument30.04.2019 added GNS430W Upgrade30.04.2019 added AFMS GFC500 Autopilot

REPORT: VB-1120 ii REVISED: APRIL 1, 2019

WARNING

EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS HANDBOOK TO APPLICABLE AIRCRAFT. THIS HAND- BOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE. SUBSEQUENT R E V I S I O N S S U P P L I E D B Y P I P E R M U S T B E PROPERLY INSERTED.

Published byTECHNICAL PUBLICATIONS

Piper Aircraft, Inc.Issued: July 2, 1979

© 1979–1986, 1988, 1990, 1993–1994, 1998, 2019 Piper Aircraft, Inc.All Rights Reserved

REPORT: VB-1120 vi-k

PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont)

Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date

Rev. 14 vi-k Added log of revision page (PR930107) vi-l Added log of revision page 9-i Added Supplement 11 to T.O.C. 9-77 Added Supplement 11 W. R. MOREU Jan. 07, 1993 Rev. 15 (PR940329) 7-i Revised T.O.C. 7-26 Relocated para. 7.39 from pg. 7-26 to page 7-27 7-26 Revised para. 7.37 added ELT info. 7-27 Added page. 7-28 Added Page. W. R. MOREU March 29, 1994

Rev. 16 (PR980402) vi-k Added Rev. 16 to L of R. 2-3 Revised Para. 2.7. 3-6 Revised Para. 3.3. 7-9 Revised Fig. 7-9. 7-10 Revised Para. 7.15. 9-75 Revised illustration. PETER E. PECK April 2, 1998

Rev. 17 ii Updated copyright. (PR190401) vi-k Added Rev. 17 to L of R. 5-3 Revised Para. 5.5. ____________ 6-i Revised Table of Contents. Eric A. Wright 8-10 Revised Para. 8.15. April 1, 2019

REVISED: APRIL 1, 2019

REPORT: VB-1120 vi-l

PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont)

Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date

PIPER AIRCRAFT CORPORATION SECTION 5PA-28-181, ARCHER II PERFORMANCE

ISSUED: JULY 2, 1979 REPORT: VB-1120 5-3REVISED: APRIL 1, 2019

5.5 FLIGHT PLANNING EXAMPLE

(a) Aircraft Loading

The first step in planning the flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 (Weight and Balance) of this handbook.

The basic empty weight for the airplane as licensed at the factory has been entered in Figure 6-5. If any alterations to the airplane have been made effecting weight and balance, reference to the aircraft logbook and Weight and Balance Record (Figure 6-7) should be made to determine the current basic empty weight of the airplane.

Make use of the Weight and Balance Loading Form (Figure 6-11) and the C.G. Range and Weight graph (Figure 6-15) to determine the total weight of the airplane and the center of gravity position.

After proper utilization of the information provided, the following weights have been determined for consideration in the flight planning example.

The landing weight cannot be determined until the weight of the fuel to be used has been established [refer to item (g)(1)].

(1) Empty Weight 1412 lbs.(2) Occupants (2 x 170 lbs.) 340 lbs.(3) Baggage and Cargo 360 lbs.(4) Fuel (6 lb./gal. x 48) 288 lbs.(5) Takeoff Weight 2400 lbs.(6) Landing Weight (a)(5) minus (g)(1), (2400 lbs. minus 129 lbs.) 2271 lbs.

The takeoff weight is below the maximum of 2550 lbs. and the weight and balance calculations have determined that the C.G. position is within the approved limits.

SECTION 5 PIPER AIRCRAFT CORPORATIONPERFORMANCE PA-28-181, ARCHER II

REPORT: VB-1120 ISSUED: JULY 2, 19795-4 REVISED: FEBRUARY 2, 1990

(b) Takeoff and Landing

After determining the aircraft loading, all aspects of takeoff and landing must be considered.

Conditions of the departure and destination airport must be acquired, evaluated and maintained throughout the flight.

Apply the departure airport conditions and takeoff weight to the appropriate Takeoff Performance graph (Figure 5-7 or 5-9) to determine the length of runway necessary for the takeoff and/or the barrier distance.

The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and, when established, the landing weight.

The conditions and calculations for the example flight are listed below. The takeoff and landing distances required for the example flight have fallen well below the available runway lengths.

Departure Destination Airport Airport

(1) Pressure Altitude 2000 ft. 2300 ft.(2) Temperature 21°C 21°C(3) Wind Component (Headwind) 10 KTS 5 KTS(4) Runway Length Available 7000 ft. 4500 ft.(5) Runway Required 950 ft.* 825 ft.**

NOTEThe remainder of the performance charts used in this flight plan example assume a no wind condition. The effect of winds aloft must be considered by the pilot when computing climb, cruise and descent performance.

*reference Figure 5-13**reference Figure 5-37

ISSUED: JULY 2, 1979 REPORT: VB-1120 6-iREVISED: APRIL 1, 2019

TABLE OF CONTENTS

SECTION 6

WEIGHT AND BALANCE

Paragraph PageNo. No.

6.1 General .................................................................................... 6-16.3 Airplane Weighing Procedure ................................................. 6-26.5 Weight and Balance Data and Record................................ 6-56.7 Weight and Balance Determination for Flight ................... 6-96.9 Instructions for Using the Weight and Balance Plotter ...... 6-12a6.11 *Equipment List ................................................................... 6-13 (a) Propeller and Propeller Accessories...................... 6-14 (b) Engine and Engine Accessories ............................ 6-15 (c) Landing Gear and Brakes ...................................... 6-17 (d) Electrical Equipment ............................................. 6-19 (e) Instruments ............................................................ 6-20 (f) Miscellaneous ........................................................ 6-21 (g) Engine and Engine Accessories (Optional Equipment) ...................................... 6-23 (h) Propeller and Propeller Accessories (Optional Equipment) ...................................... 6-23 (i) Landing Gear and Brakes (Optional Equipment) ....................................................... 6-24 (j) Electrical Equipment (Optional Equipment) ......... 6-25 (k) Instruments (Optional Equipment) ........................ 6-28 (l) Autopilots (Optional Equipment) .......................... 6-29a (m) Radio Equipment (Optional Equipment) .............. 6-29b (n) Miscellaneous (Optional Equipment) ................... 6-41

**Equipment List (Form 240-0007)...................... SUPPLIED WITH AIRCRAFT

*For 1982 and preceding models only.**For 1983 and subsequent models only.

ErikLinien

ErikLinien

Not implemented

PIPER AIRCRAFT CORPORATION SECTION 8PA-28-181, ARCHER II HANDLING, SERV & MAINT

ISSUED: JULY 2, 1979 REPORT: VB-11208-9

BRAKE SYSTEMFigure 8-1

SECTION 8 PIPER AIRCRAFT CORPORATIONHANDLING, SERV & MAINT PA-28-181, ARCHER II

REPORT: VB-1120 ISSUED: JULY 2, 19798-10 REVISED: APRIL 1, 2019

8.15 LANDING GEAR SERVICE

The three landing gears use Cleveland Aircraft Products 6.00 x 6, four-ply rating, type III tires with tubes. (Refer to paragraph 8.23).

Wheels are removed by taking off the hub cap, cotter pin, axle nut, and the two bolts holding the brake segment in place. Mark tire and wheel for reinstallation; then dismount by deflating the tire, removing the three through-bolts from the wheel and separating the wheel halves.

Landing gear oleos on the Archer II should be serviced according to the instructions on the units. The main oleos should be extended under normal static load until 4.50 ± 0.50 inches of oleo piston tube is exposed, and the nose gear should show 3.25 ± 0.25 inches. Should the strut exposure be below that required, it should be determined whether air or oil is required by first raising the airplane on jacks. Depress the valve core to allow air to escape from the strut housing chamber. Remove the filler plug and slowly raise the strut to full compression. If the strut has sufficient fluid, it will be visible up to the bottom of the filler plug hole and will then require only proper inflation.

Should fluid be below the bottom of the filler plug hole, oil should be added. Replace the plug with valve core removed; attach a clear plastic hose to the valve stem of the filler plug and submerge the other end in a container of hydraulic fluid. Fully compress and extend the strut several times, thus drawing fluid from the container and expelling air from the strut chamber. To allow fluid to enter the bottom chamber of the main gear strut housing, the torque link assembly must be disconnected to let the strut be extended a minimum of 10 inches (the nose gear torque links need not be disconnected). Do not allow the strut to extend more than 12 inches. When air bubbles cease to flow through the hose, compress the strut fully and again check fluid level. Reinstall the valve core and filler plug, and the main gear torque links, if disconnected.

With fluid in the strut housing at the correct level, attach a strut pump to the air valve and with the airplane on the ground, inflate the oleo strut to the correct height.

---------------------------------------

19 GFC500 Autopilot System

Piper PA28-181

OE-KBS 28-8390087

AFMS, Garmin G5 AML STC 190-01112-13 Rev. 5

© Copyright 2017 Garmin Ltd. or its subsidiaries

All Rights Reserved

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated,

downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin.

Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto

a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision

hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of

this copyright notice and provided further that any unauthorized commercial distribution of this manual or any

revision hereto is strictly prohibited.

Garmin International, Inc. 1200 E. 151st Street

Olathe, KS 66062 USA Telephone: 913-397-8200

www.garmin.com

http://www.garmin.com/

190-01112-13 Rev. 5 AFMS, Garmin G5 AML STC

Page i

Garmin International, Inc

Log of Revisions

FAA Approved AIRPLANE FLIGHT MANUAL SUPPLEMENT

or

SUPPLEMENTAL AIRPLANE FLIGHT MANUAL

GARMIN G5 ELECTRONIC FLIGHT INSTRUMENT

REV

NO. PAGE NO(S) DESCRIPTION

DATE OF

APPROVAL FAA APPROVED

1 ALL Original Issue 7/22/2016

Robert Murray

ODA STC Unit

Administrator

2 ALL Added information regarding G5

DG/HSI. 4/28/2017

Robert Murray

ODA STC Unit

Administrator

3 ALL Added interface to 3rd party autopilots. 10/18/2017

Robert Murray

ODA STC Unit

Administrator

4 ALL Added note to General section. 10/26/17

Paul Mast

ODA STC Unit

Administrator

5 ALL

Reformatted document. Updated

system messages interface. Added

DG/HSI reversion description.

See Cover See Cover


Page ii

This page intentionally left blank.


Page iii

Table of Contents

Section 1 – General .................................................................................................... 1-1

Abbreviations and Terminology ......................................................................................................... 1-2

Section 2 – Limitations .............................................................................................. 2-1

System Software Requirements ......................................................................................................... 2-1

Use of Secondary Instruments ........................................................................................................... 2-1

Kinds of Operations ............................................................................................................................. 2-1

Section 3 – Emergency Procedures ......................................................................... 3-1

G5 Failure Indications .......................................................................................................................... 3-1

Attitude Failure .................................................................................................................................... 3-1

Heading Failure, Loss of Magnetometer Data, or Magnetic Field Error ............................................. 3-1

GPS Failure ........................................................................................................................................ 3-2

Attitude Aligning ................................................................................................................................... 3-2

Attitude Aligning / Keep Wings Level ................................................................................................. 3-2

Loss of Electrical Power to the G5 Display ....................................................................................... 3-2

Loss of Electrical Power to the GAD 29B (If Installed) ..................................................................... 3-3

Section 4 – Normal Procedures ................................................................................ 4-1

G5 Power Button and Knob ................................................................................................................. 4-1

Backlight Intensity Adjustment ........................................................................................................... 4-1

Prior to Flight in Instrument Meteorological Conditions .................................................................. 4-1

Autopilot Operations with the G5 HSI ................................................................................................ 4-2

Course / NAV Selection Coupling to the Autopilot (If Configured) ..................................................... 4-2

Heading Bug Coupling Capability to the Autopilot (If Configured) ...................................................... 4-2

Roll Steering (GPSS) Emulated via HDG Mode (If Configured) ......................................................... 4-2

Section 5 – Performance ........................................................................................... 5-1

Section 6 – Weight and Balance ............................................................................... 6-1

Section 7 – System Description ................................................................................ 7-1

System Messages ................................................................................................................................. 7-1


Page iv



Page 1–1

SECTION 1 – GENERAL

The G5 Electronic Flight Instrument can display the following information to the pilot depending on the installation

and location of the G5 instrument.

• Primary attitude

• Primary slip and turn rate information

• Primary heading

• Secondary airspeed

• Secondary altimeter

• Secondary ground track

When installed in place of the attitude indicator, the primary function of the G5 is to provide attitude information to

the pilot. When installed in place of the rate of turn indicator, the primary function of the G5 is to provide turn

rate and slip ball information to the pilot. When installed in place of the directional gyro, the primary function of

the G5 is to provide directional information to the pilot.

NOTE:

The pilot is reminded to perform appropriate flight and navigation instrument cross checks for the

type of operation being conducted.

In case of a loss of aircraft electrical power, a backup battery (optional when installed as a DG/HSI) sustains the

G5 Electronic Flight Instrument for up to four hours.

An optional GAD 29B may be installed to provide course and heading datum to an autopilot based on the data

selected for display on the HSI.


Page 1–2

Abbreviations and Terminology

The following glossary is applicable within the airplane flight manual supplement

ADI Attitude Direction Indicator

AFMS Airplane Flight Manual Supplement

ATT Attitude

CDI Course Deviation Indicator

DG Directional Gyro

DR Dead Reckoning

FAA Federal Aviation Administration

GPS Global Positioning System

GPSS GPS Roll Steering

HDG Heading

HSI Horizontal Situation Indicator

ILS Instrument Landing System

LOC Localizer (no glideslope available)

LOI Loss of Integrity

VFR Visual Flight Rules

VHF Very High Frequency

VOR VHF Omni-directional Range


Page 2–1

SECTION 2 – LIMITATIONS

System Software Requirements

The G5 must utilize the following or later FAA approved software versions for this AFMS revision to be applicable:

Component Software Version

G5 Electronic Flight Instrument 5.00

Use of Secondary Instruments

The original type design approved instruments for airspeed, altitude and vertical speed remain the primary

indications for these parameters.

If the G5 Electronic Flight Instrument is installed in place of the rate of turn indicator, the original type design

approved instrument for attitude remains in the primary indication for attitude.

If the G5 Electronic Flight Instrument is installed in place of the directional gyro, the original type design approved

instruments for attitude remains the primary indication for attitude.

NOTE:

For aircraft approved for VFR-only operations, the G5 Electronic Flight Instrument may be

installed as an attitude indicator and rate of turn indicator.

Kinds of Operations

No Change.


Page 2–2



Page 3–1

SECTION 3 – EMERGENCY PROCEDURES

G5 Failure Indications

If a G5 function fails, a large red ‘X’ is typically displayed over the instrument(s) or data experiencing the failure.

Upon G5 power-up, certain instruments remain invalid as equipment begins to initialize. All instruments should

be operational within one minute of power-up. If any instrument remains flagged and it is not likely an installation

related problem, the G5 should be serviced by a Garmin-authorized repair facility.

Attitude Failure

Attitude failure is indicated by removal of the sky/ground presentation, a red X, and a yellow “ATTITUDE FAIL” on

the display.

Rate-of-turn and slip information will not be available.

1. Use standby instruments.

2. Seek VFR conditions or land as soon as practical.

Heading Failure, Loss of Magnetometer Data, or Magnetic Field Error

A heading failure, loss of magnetometer data, or magnetic field error is indicated by removal of the digital heading

readout, a red X, and a yellow “HDG” on the display.

1. Use standby magnetic compass.

NOTE:

If the G5 DG/HSI has a valid GPS signal the G5 DG/HSI instrument will display the GPS track

information in magenta.


Page 3–2

GPS Failure

If GPS navigation receivers and/or navigation information are not available or invalid, the G5 will display Dead

Reckoning mode (DR) or Loss of Integrity mode (LOI) on the HSI in the lower left corner.

If Alternate Navigation Sources (ILS, LOC, VOR) Are Available:

1. Use alternate navigation source.

If No Alternate Navigation Sources Are Available:

If DR is Displayed on HSI:

1. Use the amber CDI for course information.

2. Fly toward known visual conditions.

If LOI is Displayed on HSI:

1. Fly toward known visual conditions.

For aircraft equipped with a GAD 29B interfaced to an autopilot, GPSS will be displayed in amber text when GPSS

emulation has been selected from the G5 menu.

1. Deselect GPSS from the G5 menu and select a different autopilot mode.

Attitude Aligning

During system initialization, the G5 displays the message ‘ALIGNING’ over the attitude indicator. The G5 will

typically display valid attitude within the first minute of power-up. The G5 can also align itself while taxiing and

during level flight.

If the “ALIGNING” indication occurs during flight and attitude remains displayed, the attitude display is acceptable

for use for flight in instrument conditions. The message will clear when the attitude solution is within the systems

internal accuracy tolerances. It is recommended to maintain wings level to reduce the time for the system to

align.

Attitude Aligning / Keep Wings Level

If the “ALIGNING KEEP WINGS LEVEL” indication occurs during flight, the G5 has detected an invalid attitude

solution and will not display any attitude information.

1. Use standby instruments to maintain wings level flight. The system will display attitude when internalaccuracy tolerances have been met.

2. If attitude does not return, seek VFR conditions or land as soon as practical.

Loss of Electrical Power to the G5 Display

In the event of a loss of aircraft electrical power to the G5 attitude display, the indicator will continue to function on

its internal battery. If an internal battery is installed on the optional G5 HSI, the indicator will continue to function

on the internal battery if aircraft power is lost. Internal battery endurance is indicated on the G5 display in hours

and minutes. The charging symbol will be removed and the internal battery will not be charged.

In the event the G5 attitude display powers down, the optional G5 HSI will automatically revert to displaying

attitude information. It will not revert back to the DG/HSI format if the G5 attitude unit regains power. The

DG/HSI presentation may be selected from the G5 menu on the G5 DG/HSI unit after reversion to the attitude

display.


Page 3–3

Loss of Electrical Power to the GAD 29B (If Installed)

In the event of a loss of aircraft electrical power to the optional GAD 29B, the heading and course datum will be

unavailable to the autopilot and the autopilot may deviate from the intended path or may disconnect. GPS flight

plan course information may be displayed on the HSI and VFR will be displayed in amber text on the HSI. GPSS

will be displayed in amber text, if GPSS mode is selected.

1. Deselect GPSS from the G5 menu and select a different autopilot mode.

2. Lateral GPS course guidance may only be used in VFR conditions.


Page 3–4



Page 4–1

SECTION 4 – NORMAL PROCEDURES

G5 Power Button and Knob

The G5 display will power on with the application of aircraft power. The G5 power button is used to turn the

display on and off. Press and hold the power button to turn the display off.

The knob performs the following functions:

Press

Press to access the Menu.

From the Menu, press to select the desired menu item.

Press to accept the displayed value when editing numeric data or selecting from a list.

Press to sync the heading or track bug for the HSI.

Turn

From the Menu, turn the Knob to move the cursor to the desired menu item.

For the ADI, rotate to adjust the baro setting on the secondary altitude display.

For the HSI, rotate to adjust the heading or track bug.

Turn to select the desired value when editing numeric data or selecting from a list.

Backlight Intensity Adjustment

The power up state of the G5 backlight is in Auto adjustment mode.

To adjust the backlighting:

To select Manual mode from Auto mode:

1. While the unit is turned on, press the Power button.

2. Turn the knob to manually adjust the backlight intensity.

3. Press the knob to close the backlight page.

To select Auto mode from Manual mode:

1. While the unit is turned on, press the Power button.

2. Press the Power button again to select Auto.

3. Press the knob to close the backlight page.

Prior to Flight in Instrument Meteorological Conditions

1. Press the Power button on the G5 attitude indicator.

2. Verify the battery status indicator is green on the G5 attitude indicator.


Page 4–2

Autopilot Operations with the G5 HSI

The G5 and optional GAD 29B offer various integration capabilities dependent upon the type of autopilot installed

in a particular aircraft.

The G5 Electronic Flight Instrument installation in this aircraft provides the following autopilot functions

(appropriate boxes will be checked):

This installation does not interface with the autopilot (basic wing leveling autopilot or no autopilot is installed in the aircraft).

A GAD 29B Adapter is installed in this aircraft.

Course / NAV Selection coupling to the autopilot.

Heading Bug coupling capability to the autopilot.

Roll Steering (GPSS) emulated via heading mode.

OR

Roll Steering capable autopilot (GPSS menu function for emulation not applicable).

Course / NAV Selection Coupling to the Autopilot (If Configured)

When operating the autopilot in NAV mode, the deviation information from the installed navigation sources (i.e.

GPS or NAV) is switched via the navigation source. The NAV source displayed on the HSI is the NAV source

the autopilot is following. Many autopilots also use the course datum to determine the best intercept angles

when operating in NAV mode.

Heading Bug Coupling Capability to the Autopilot (If Configured)

When operating the autopilot in HDG mode, the difference between the HDG bug location on the HSI and the

actual aircraft heading creates an error signal which the autopilot will minimize by turning in the direction of the

bug. If the bug is turned more than 180 degrees, the autopilot may turn the airplane in the opposite direction of

the desired turn.

Roll Steering (GPSS) Emulated via HDG Mode (If Configured)

For autopilots that do not support digital GPSS signals, GPSS functionality may be emulated by operating the

autopilot in HDG mode and selecting GPSS from the G5 menu. If the autopilot is already designed to receive roll

steering information, the data is transmitted digitally from the navigator to the autopilot.

When GPSS is selected on the G5 menu, the heading bug on the HSI changes to a hollow outline and a crossed-

out heading bug appears on the G5 HSI display indicating that the autopilot is not coupled to the heading bug.

The bug is still controllable and may still be used for reference.

When GPSS is selected on the G5, GPSS turn commands are converted into a heading error signal to the

autopilot. When the autopilot is operated in HDG mode, the autopilot will fly the turn commands from the GPS

X


Page 4–3

navigator. If the GPSS data is invalid (for example, if there is no active GPS leg) or the selected HSI source on

the G5 HSI is not GPS, the annunciated GPSS text will be yellow and a zero turn command will be sent to the

autopilot.


Page 4–4



Page 5–1

SECTION 5 – PERFORMANCE

No change.


Page 5–2



Page 6–1

SECTION 6 – WEIGHT AND BALANCE

See current weight and balance data.


Page 6–2



Page 7–1

SECTION 7 – SYSTEM DESCRIPTION

Refer to Garmin G5 Electronic Flight Instrument Pilot’s Guide for Certified Aircraft, part number 190-01112-12

Rev A (or later approved revisions), for a description of the G5 electronic flight instrument. This reference

material is not required to be on board the aircraft but does contain a more in depth description of all the functions

and capabilities of the G5.

The ATT circuit breaker supplies power to the G5 instrument for normal power operation and to charge the

internal battery.

The DG circuit breaker supplies power to the G5 instrument for normal power operation when configured as a

DG, and to charge the internal battery (if installed).

The HSI circuit breaker supplies power to the G5 instrument for normal power operation when configured as an

HSI, and to charge the internal battery (if installed).

The GAD circuit breaker supplies power to the optional GAD 29 adapter for normal power operation.

System Messages

The G5 has the capability to display system messages to the crew along the bottom of the display. A system

message is indicated through a white indication on the G5.

Messages can be displayed by pressing the G5 knob, and selecting the Message menu item.

(For Reference Only)


Page 7–2

The following table shows the meaning of each message. System messages are displayed in white text.

Message Meaning

External Power Lost Aircraft power has been removed from the G5.

Critical battery fault!

Powering off

Battery has critical fault condition and the unit is about to power off to avoid

damage to the battery.

Battery fault Battery has a fault condition – unit needs service.

Battery charger fault Battery charger has a fault condition – unit needs service.

Low battery Battery charge level is low.

Hardware fault Unit has a hardware fault – unit needs service.

Power supply fault Unit power supply fault detected – unit needs service.

Unit temperature limit

exceeded Unit is too hot or too cold.

Network address

conflict

Another G5 with the same address is detected on the network (most commonly

a wiring error on one of the units).

Communication error General communication error (most commonly appears in conjunction with

Network Address Conflict message).

Factory calibration

data invalid Unit calibration data not valid – unit needs service.

Magnetic field model

database out of date Internal magnetic field database is out of date - software update required.

Magnetometer

Hardware fault

The magnetometer has detected a fault – unit needs service. Heading data

may not be available.

Using external GPS

data

GPS data from another network LRU is being used. The unit's internal GPS

receiver is enabled, but unable to establish a GPS fix.

Not receiving RS-232

data

The G5 is not receiving RS-232 data from the GPS navigator – system needs

service.

Not receiving ARINC

429 data

The G5 is not receiving ARINC 429 data from the navigation source – system

needs service.

GPS receiver fault The G5 on-board GPS receiver has a fault.

ARINC 429 interface

configuration error

The G5 ARINC 429 port is receiving information from an incorrect source –

system needs service.

Software version

mismatch

The G5 attitude indicator and the G5 HSI units have different software. Cross

fill of baro, heading and altitude bugs is disabled.

These messages remain while the condition persists.

Archer II_POH VB-1120_Rev. 17.pdfvb1120 _rev17 RevNote 190401vb1120 r17 i_ii 190401vb1120 r17 vi-k_vi-l 190401vb1120 r17 5- 3_5-4 190401vb1120 r17 6- i_6-ii 190401vb1120 r17 8- 9_8-10 190401

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